Including Vibration Control Patents (Class 244/173.2)
-
Patent number: 11565628Abstract: A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module. The cargo module of the cargo spacecraft is positioned along the launch vehicle axis in a direction distal from the support structure, and at least a portion of the service module of the cargo spacecraft positioned within an annulus of the support structure.Type: GrantFiled: March 29, 2019Date of Patent: January 31, 2023Assignee: Blue Origin, LLCInventor: Michael David Johnson
-
Patent number: 11492144Abstract: The invention relates to a flywheel for stabilising the position of a spacecraft, comprising a hub means (1) for fastening the flywheel, a flywheel ring (4), which externally surrounds the hub means (1) circumferentially at a distance, a support means (3) for supporting the flywheel ring (4) on the hub means (1), and a vibration damping device (6, 8) having a tuned mass damper means (8) which is axially movable back and forth relative to the flywheel ring with respect to a rotation axis of the flywheel.Type: GrantFiled: May 6, 2019Date of Patent: November 8, 2022Assignee: ROCKWELL COLLINS DEUTSCHLAND GMBHInventors: Markus Ehinger, Dirk Henning
-
Patent number: 10562650Abstract: A spacecraft. The spacecraft includes a rocket engine; a first stage connected to the rocket engine; and a payload stage connected to the first stage. The spacecraft also includes a payload structure inside the payload stage between a first compartment of the payload stage and a second compartment of the payload stage. The payload structure may be a single shell that has a corrugated shape such that an inside surface and an outside surface of the payload structure vary in shape to form the corrugations.Type: GrantFiled: June 28, 2017Date of Patent: February 18, 2020Assignee: The Boeing CompanyInventors: Richard Forrest Ewing, Robert Lane
-
Patent number: 9840012Abstract: In one embodiment, a selectable-rate spring comprises a flexure bar connected to a rotatable shaft, the flexure bar having at least one arched portion. The selectable-rate spring also includes at least one rotational contactor connectable to a link member, wherein the rotational contactor rotates about an axis while maintaining contact with the arched portion of the flexure bar. As the rotational contactor rotates, it changes the connection stiffness between the rotatable shaft and the link member.Type: GrantFiled: April 24, 2014Date of Patent: December 12, 2017Assignee: Marquette UniversityInventors: Joseph M. Schimmels, Daniel Garces
-
Patent number: 9791014Abstract: In one embodiment, a vibration control apparatus is provided having a pair of face sheets with a core material in between. The core material comprising a positive stiffness material. A stack comprising a positive stiffness structure in series with a negative stiffness structure is located between the pair of face sheets, in parallel with the core material. The stack may be embedded in the core material. Various embodiments may include multiple stacks in parallel with each other. In some embodiments, the stack may include multiple positive stiffness structures in series with multiple negative stiffness structures. The multiple positive stiffness structures and negative stiffness structures may be interleaved.Type: GrantFiled: March 15, 2013Date of Patent: October 17, 2017Assignee: HRL Laboratories, LLCInventors: Geoffrey P. McKnight, Chia-Ming Chang, Andrew C. Keefe, William Carter
-
Patent number: 9618072Abstract: A shock damping element includes a first shock damping structure that includes a multitude of first elements, a multitude of second elements and a first central member. The first elements and the second elements are located at opposite sides of the first central member. The first and second elements extend towards the first central member at a first acute angle (?) relative the first central member and are connected to the first central member. The first and second elements extend in a first direction circumferentially.Type: GrantFiled: August 27, 2015Date of Patent: April 11, 2017Assignee: RUAG SPACE ABInventors: Michael Thuswaldner, Anders Helmersson, Orjan Arulf
-
Patent number: 9394064Abstract: The invention relates to a load bearing interface ring (1) for a space craft. The load bearing interface ring (1) comprises a first part (3) and a second part (4). The first part (3) is arranged to carry compression loads and is mounted on an inside surface (11) of the second part (4). The second part (4) is arranged to carry shear and global bending loads. The second part (4) comprises at least two laminate plies (8), where the laminate plies (8) are oriented in a normal plane (12) of a jacket surface (5) of the load bearing interface ring (1).Type: GrantFiled: May 7, 2013Date of Patent: July 19, 2016Assignee: RUAG SPACE ABInventors: Orjan Arulf, Magnus Persson, Michael Thuswaldner
-
Patent number: 9038961Abstract: A method for simulating the movement behavior of a fluid in a closed moving container is provided. The simulation is based on the determination of the potential movement path of the center of gravity of the volume of the fluid as an elliptical trajectory situated in a disturbance plane having certain semi-axes.Type: GrantFiled: December 9, 2010Date of Patent: May 26, 2015Assignee: EADS Deutschland GmbHInventor: Ronald Deslandes
-
Patent number: 8939409Abstract: An adaptor system includes a space vehicle separation plate operably coupled to a space vehicle, a launch vehicle adaptor plate operably coupled to a launch vehicle capable of carrying the space vehicle into space for release of the space vehicle from the launch vehicle, an actuator release mechanism assembly, a bend/shear restrain assembly that is non-coaxial with the actuator-release connector, and a biasing element. The actuator-release mechanism assembly may be configured to separably couple the space vehicle separation plate to the launch vehicle adaptor plate. The actuator-release mechanism assembly may pass through the launch vehicle adaptor plate to engage the space vehicle separation plate to hold the space vehicle separation plate substantially parallel to the launch vehicle adaptor plate prior to release of the space vehicle separation plate.Type: GrantFiled: May 6, 2013Date of Patent: January 27, 2015Assignee: The Johns Hopkins UniversityInventors: Clint T. Apland, Aaron Q. Rogers, David F. Persons, Robert A. Summers
-
Publication number: 20140332632Abstract: An adapter arrangement includes a first adapter ring for interfacing with a launch vehicle payload interface ring, a second adapter ring for interfacing with a payload launch vehicle interface ring, and a plurality of vibration isolation devices disposed between and attached to each of the first adapter ring and the second adapter ring. The first adapter ring has a first standard interface with the launch vehicle payload interface ring and the second adapter ring has a second standard interface with the payload launch vehicle interface ring.Type: ApplicationFiled: December 6, 2013Publication date: November 13, 2014Applicant: Space Systems/Loral, LLCInventors: Robert E. Helmer, Hauke G. Nehrenheim
-
Publication number: 20140291452Abstract: Embodiments of an isolator are provided, as are embodiments of a spacecraft isolation system employing a number of three parameter isolators. In one embodiment, the isolator includes an externally-pressurized damper assembly and a thermal compensator, which is located external to the externally-pressurized damper assembly. The damper assembly includes, in turn, a damper assembly housing and a first hydraulic chamber configured to be filled with a damping fluid. The first hydraulic chamber is located within the damper assembly housing and is fluidly coupled to the thermal compensator. A first bellows is disposed within the damper assembly housing and bounds an inner circumference of the first hydraulic chamber such that the first bellows is externally pressurized when the first hydraulic chamber is filled with the damping fluid.Type: ApplicationFiled: March 27, 2013Publication date: October 2, 2014Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Daniel Martinez, Jose Pagan, Cesar Arroyo
-
Patent number: 8727299Abstract: The assembly for an aircraft comprises: at least one device; a part such as a support; and at least one damper via which the device bears against the part, the damper comprising carbon nanotubes covered at at least one of their ends by a layer having a diamond type crystal structure.Type: GrantFiled: September 23, 2011Date of Patent: May 20, 2014Assignee: Airbus (S.A.S.)Inventor: Philippe Tatry
-
Publication number: 20140084113Abstract: Launch lock assemblies with reduced preload are provided. The launch lock assembly comprises first and second mount pieces, a releasable clamp device, and a pair of retracting assemblies. Each retracting assembly comprises a pair of toothed members having interacting toothed surfaces. The releasable clamp device normally maintains the first and second mount pieces in clamped engagement. When the releasable clamp device is actuated, the first and second mount pieces are released from clamped engagement and one toothed member of each retracting assembly moves in an opposite direction relative to the other one toothed member of the other retracting assembly to define an axial gap on each side of the first mount piece.Type: ApplicationFiled: September 25, 2012Publication date: March 27, 2014Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Tim Daniel Barber, Ken Young, Timothy Hindle
-
Publication number: 20130284857Abstract: An object is to provide an adaptor that can attenuate a vibration acting on a payload using a simple structure, and a payload launch vehicle. The adaptor (1) according to the invention controls a vibration of the payload housed in the payload launch vehicle, and is provided between the payload and a rocket portion. The adaptor (1) includes a cylinder member having a double structure including an outer cylinder (11) and an inner cylinder (12); a first elastic member (21) coupled to the outer cylinder (11) and the inner cylinder (12) at one end of the cylinder member; and a second elastic member (22) coupled to the outer cylinder and the inner cylinder at the other end of the cylinder member. The adaptor (1) is linked to the payload on the inner cylinder side or the outer cylinder side on one end side of the cylinder member, and linked to a leading end of the rocket portion on the outer cylinder side or the inner cylinder side on the other end side of the cylinder member.Type: ApplicationFiled: December 15, 2011Publication date: October 31, 2013Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventor: Toshihiro Tombe
-
Patent number: 8532847Abstract: A vibration suppressing device for a spacecraft. A plurality of spacecraft deflection sensors measure a plurality of spacecraft deflections at specified locations on a spacecraft structure. A spacecraft modal coordinate calculation unit calculates a plurality of spacecraft modal coordinates. A high pass filter extracts a plurality of fluctuations of spacecraft modal coordinates. A cost function calculation unit calculates a cost function as a function of the plurality of fluctuations of spacecraft modal coordinates. A payload position calculation unit calculates an optimal payload position minimizing the cost function. A payload position adjustment device generates a control input suppressing a vibration transmitted to the payload system, and adjusts the payload position to the optimal payload position.Type: GrantFiled: September 28, 2012Date of Patent: September 10, 2013Inventor: Fukashi Andoh
-
Patent number: 8401717Abstract: The aim of the method of controlling at least one mechanical system exhibiting at least one flexible structure element and at least one actuator or group of actuators is to reduce the level of vibrations of said element while controlling the actuator or group of actuators in such a way as to achieve at least one objective assigned to the mechanical system. The control consists of increments having to be carried out at a sampling period T, each of the increments being constant in amplitude in a sampling time interval extending between two successive sampling instants and each of the increments being applied during a duration which is less than or equal to the sampling period T. In each sampling interval, at least one of the initial and final instants of application of the increment is modified by adding a variable, random or pseudo-random, temporal deviation dT.Type: GrantFiled: March 5, 2008Date of Patent: March 19, 2013Assignee: Astrium SASInventor: Philippe Guyot
-
Patent number: 8371534Abstract: A system for isolating vibration among a plurality of instruments on a spacecraft includes at least two platforms, each of which is configured to couple to and isolate vibration for a single one of the plurality of instruments. Each of the at least two platforms is configured to mount to the spacecraft. A device is also provided for isolating vibration for one instrument among a plurality of instruments on a spacecraft.Type: GrantFiled: August 6, 2008Date of Patent: February 12, 2013Assignees: Lockheed Martin Corporation, Honeywell International, Inc.Inventors: Neil E. Goodzeit, Harald J. Weigl, Michael Brett McMickell, Timothy Andrew Hindle
-
Patent number: 8240614Abstract: The device comprises at least three isolating modules each having two rigid pieces, one of which is fastened to the carrier structure and the other of which is fastened to the support for the vibrating equipment, these pieces being linked by at least one isolating stud made of an elastomer, which attenuates the transmission of low-amplitude vibrations from the equipment to the structure, the deformation of at least one stud in tension-compression and in shear being limited by three flexible stops each mounted on only one of the pieces and the free end of which is facing the other of said pieces and not in contact with it, at rest. Each stop comprises an elastomer element coming into contact with the facing other piece during deformations of sufficient amplitude of the isolating stud, the stiffness of the elastomer of the stop being greater than that of the stud. Application to the isolation of vibrating equipment on a satellite carrier structure.Type: GrantFiled: December 21, 2006Date of Patent: August 14, 2012Assignee: Astrium SASInventor: Patrick Camarasa
-
Publication number: 20120061520Abstract: A frangible joint structure includes shock attenuation features formed as an integral part of the joint structure. Shock attenuation is achieved through use of, for example, slots or grooves that are machined directly, or otherwise formed integrally, into the frangible joint structure. Adequate shock attenuation is achieved solely by the features machined or otherwise formed in the frangible joint together with the typical assembly of the frangible joint into various structures (e.g., as a payload separator for rockets, missiles, satellites, etc.), without the need for additional hardware components and thus without the need for assembly of the frangible joint shock attenuation device.Type: ApplicationFiled: July 13, 2009Publication date: March 15, 2012Applicant: ENSIGN-BICKFORD AEROSPACE & DEFENSE COMPANYInventor: John A. Graham
-
Patent number: 7905453Abstract: The invention relates to piggyback secondary payloads, a device for and a method of attaching piggyback secondary payloads, including a primary satellite and at least one secondary payload, such as a deployable microsatellite, affixed instrument package or the like, wherein the secondary payload is mounted on the nadir end of the primary satellite, preferably employing a universal adapter between the primary satellite and the at least one secondary payload.Type: GrantFiled: April 30, 2007Date of Patent: March 15, 2011Assignee: IntelsatInventors: Bryan Benedict, Gerard Jansson
-
Patent number: 7866607Abstract: The invention relates to a piggyback satellite, a device for and a method of attaching piggyback satellites with multiple payloads, including a primary satellite and at least one secondary payload, such as a deployable micro satellite, affixed instrument package or the like, wherein the secondary payload is mounted on the nadir end of the primary satellite, preferably employing a universal adapter between the primary satellite and the at least one secondary payload that releases at least one secondary payload or the like in a certain orbit in space for allowing the secondary payload to continue its journey independently in space for transmitting and receiving data.Type: GrantFiled: April 30, 2007Date of Patent: January 11, 2011Assignee: IntelsatInventor: Bryan Benedict
-
Patent number: 7762194Abstract: An apparatus that provides shock absorption and ejection for a payload that is to be deployed from a launch capsule is disclosed. The payload ejection mechanism comprises a movable housing that houses a resilient member and a shock-damping system. The rapid acceleration of the capsule upon launch causes the movable housing to move, which compresses the resilient member, thereby storing energy. Movement of the housing also provides shock damping behavior. A locking mechanism maintains the compression of the resilient member until the capsule opens to deploy the payload. As the capsule opens, a restraint decouples from the locking mechanism and permits the resilient member to expand. Expansion of the resilient member causes the movable housing to move, thereby propelling the payload away from the capsule.Type: GrantFiled: September 12, 2006Date of Patent: July 27, 2010Assignee: Lockheed Martin CorporationInventor: Randy L. Gaigler
-
Publication number: 20100020742Abstract: Various aspects of the disclosure provide hybrid spacecraft capable of hosting both a remote sensing payload and a communications payload. A hybrid spacecraft includes an isolation system for a remote sensing payload that isolates the remote sensing payload from spacecraft dynamics and disturbances, and prevents interaction between the remote sensing and communications payloads. The hybrid spacecraft may also include provisions for a communications payload including metering structure for large aperture antennas, and scalable resources for accommodating a range of remote and communications payloads.Type: ApplicationFiled: July 20, 2009Publication date: January 28, 2010Applicant: Lockheed Martin CorporationInventors: Neil E. Goodzeit, Harald J. Weigl, John C. Petheram, Andy A. Santoro
-
Patent number: 7513462Abstract: A satellite payload structure includes one side that includes at least two equipment mounting panels. Each of the equipment mounting panels are oriented substantially parallel to each other such that when the satellite is deployed, each of the equipment mounting panels are substantially parallel to a vector pointing from the deployed location of the satellite to a point on the earth's surface. The point on the earth's surface is located vertically beneath the satellite such that the vector is substantially normal to the earth's surface.Type: GrantFiled: June 8, 2005Date of Patent: April 7, 2009Assignee: Lockheed Martin CorporationInventors: Douglas V. McKinnon, David J. Hentosh
-
Publication number: 20090008504Abstract: The device comprises at least three isolating modules each having two rigid pieces, one of which is fastened to the carrier structure and the other of which is fastened to the support for the vibrating equipment, these pieces being linked by at least one isolating stud made of an elastomer, which attenuates the transmission of low-amplitude vibrations from the equipment to the structure, the deformation of at least one stud in tension-compression and in shear being limited by three flexible stops each mounted on only one of the pieces and the free end of which is facing the other of said pieces and not in contact with it, at rest. Each stop comprises an elastomer element coming into contact with the facing other piece during deformations of sufficient amplitude of the isolating stud, the stiffness of the elastomer of the stop being greater than that of the stud. Application to the isolation of vibrating equipment on a satellite carrier structure.Type: ApplicationFiled: December 21, 2006Publication date: January 8, 2009Applicant: ASTRIUM SASInventor: Patrick Camarasa
-
Patent number: 7424989Abstract: Circuits and methods for use on a mobile platform including a flight control system, a structure, an aerodynamic surface, and an actuator operatively coupled to the surface to control the surface. The circuit includes a first and a second input, a summing element, and an output. The first input accepts commands from the flight control system while the second input accepts a vibration signal from the structure. The summing element communicates with the inputs and sums the signal and the command. In turn, the summing element controls the actuator with the summed signal and command.Type: GrantFiled: March 11, 2004Date of Patent: September 16, 2008Assignee: The Boeing CompanyInventor: Dale M. Pitt
-
Patent number: 7421343Abstract: Systems and methods for reducing vibration-induced bias errors in inertial sensors are disclosed. A system for reducing bias errors in an inertial sensor operating within an environment may include a vibration detector for sensing vibration changes within the environment proximate to the inertial sensor, and a Kalman filter for computing an estimate of the navigational error produced by the inertial sensor due to a vibration-induced bias shift detected by the vibration detector. The vibration detector can be configured to measure an accelerometer output of the inertial sensor over a Kalman filter cycle, and then use the standard deviation of such output to obtain a statistical measure of the vibration within the environment. In some embodiments, the inertial sensor may include an inertial measurement unit (IMU) connected to an error compensation unit and strapdown navigator, each of which can be fed navigation corrections determined by the Kalman filter.Type: GrantFiled: October 27, 2005Date of Patent: September 2, 2008Assignee: Honeywell International Inc.Inventor: Wesley J. Hawkinson
-
Publication number: 20080078887Abstract: An apparatus that provides shock absorption and ejection for a payload that is to be deployed from a launch capsule is disclosed. The payload ejection mechanism comprises a movable housing that houses a resilient member and a shock-damping system. The rapid acceleration of the capsule upon launch causes the movable housing to move, which compresses the resilient member, thereby storing energy. Movement of the housing also provides shock damping behavior. A locking mechanism maintains the compression of the resilient member until the capsule opens to deploy the payload. As the capsule opens, a restraint decouples from the locking mechanism and permits the resilient member to expand. Expansion of the resilient member causes the movable housing to move, thereby propelling the payload away from the capsule.Type: ApplicationFiled: September 12, 2006Publication date: April 3, 2008Applicant: LOCKHEED MARTIN CORPORATIONInventor: Randy L. Gaigler
-
Patent number: 7249756Abstract: The invention disclosed is a low-profile, multi-axis, highly passively damped, vibration isolation mount which when used in multiplicity provides a complete vibration load isolation mounting system. The device provides in unique fashion a very low profile interface in combination with independently determinable compliance in all directions of vibration loading. Substantial passive damping is afforded without sacrifice to strength and linearity of behavior through adaptation of a shear wall type constrained layer damping. The result is a highly passively damped vibration isolation device that provides a very low profile interface, wide ranging longitudinal and lateral compliance management, in a durable, reliable, lightweight, and compact form.Type: GrantFiled: February 1, 2006Date of Patent: July 31, 2007Assignee: CSA Engineering, Inc.Inventors: Paul S. Wilke, Conor D. Johnson
-
Patent number: 7222823Abstract: A payload adapter consists of a body that when hollow includes a plurality of stiffeners—radial and/or circumferential—or alternatively a core for carrying shear loads. The body may include a first annular face sheet, a second annular face sheet and a plurality of stiffeners connecting between the first annular face sheet and the second annular face sheet. The combination of the annular hollow body and the plurality of stiffeners or the same face sheets combined with an in-filled core results in an axial frequency and a lateral (pitch) frequency for the payload adapter that provides superior vibration isolation. Constrained layer damping is incorporated into the design for additional vibration attenuation.Type: GrantFiled: July 6, 2004Date of Patent: May 29, 2007Assignee: ATA Engineering, Inc.Inventors: Gareth Rhys Thomas, Cynthia Marie Fadick
-
Patent number: 7093806Abstract: A method and system for calculating a control function for a structural system (10) that can be used to determine an appropriate control force to apply to an active member (18) within a stationary member (12) on the structural system (10). An active member (18) and a stationary member (12) are defined as a two-mass system in which the active member (18) and the stationary member (12) move in opposite directions. The stationary member (12) is mounted to an isolation subsystem (14) that is composed of six isolators (28) at multiple degrees of freedom. The isolation subsystem (14) is softer than the stationary member (12), active member (18) and a spacecraft surface (16) due to a damping element (32) of the isolation subsystem (16). The isolation subsystem (16) is mounted to the spacecraft (16) and decouples the spacecraft (16) from the stationary member (12) and thus the active member (18). An accurate control force for the active member (18) can be determined based upon the above structure (10).Type: GrantFiled: May 20, 2004Date of Patent: August 22, 2006Assignee: Honeywell International, Inc.Inventor: David A. Osterberg
-
Patent number: 7090171Abstract: A spacecraft system including a spacecraft assembly or “stack” having an upper stage of a rocket-powered launch vehicle providing a final boost phase during launch. The stack also includes a payload structure rotatably interconnected with the upper stage. The upper stage and the payload structure together define a central axis that is generally coincident with the thrust axis during launch. The stack has an axis of maximum moment of inertia that is not parallel to the central axis. The stack has internal damping such that unstable nutation occurs if the upper stage and the payload structure rotate together about the central axis at the same rotational rate and in the same direction. The system includes a controller that rotates the payload structure relative to the upper stage during the final boost phase to alleviate coning motion of the stack.Type: GrantFiled: April 30, 2003Date of Patent: August 15, 2006Assignee: Honeywell International, Inc.Inventor: Mason A. Peck